Aircraft control



Cat. 22, 1929. w. s. DIEHL AIRCRAFT CONTROL 3 Sheets-Sheet Filed April 15. 192

Oct. 22, 1929. w, s HL AIRCRAFT CONTROL Filed April 15 192 5 Sheets-Sheet 'JNVENTOR WuTE/P 5 3151%,

AT'TOFPNEY Oct. 22, 1929. w. s. DlEHL AIRCRAFT CONTROL Filed April 15 192' I5 Sheets-Sheet R m N m N 1 W LTER 5'. ,D/EHL M BY a ATTORNEY Patented Oct. 22, 1 929 UNITED STATES PATENT OFFICE wanr'aa a. menu, or

(enmren mm My invention relates bro parti'cula control. 7 a An object of my invention is to provide an wing having attached thereto an adch the aileron is ad control and more construction and 5 aircraft ustablsection' to whi justably attached.

Another object of my inventionvide a means for pivotally raising .w ing an intermediate section of a wing and dual multaneously and in the sam by changing the Win a high lift wing,

the ailerons.

WABHINGTON, DISTRICT OF COLUMBIA AIRCRAFT CONTROL m 501 or MARCH 3,

control of the aircraft.

With the above and other the invention consists in th combination and arrangeme $55 will be hereinafter more fully described.

Reference is to be had to t drawings forming part of in which like reference ch corresponding 55% views, and

wing showing the aileron arranged as Figure 3 is a top merit between the aileron, hill Figure 5 IS a tween these parts,

lt igure 6 is a schematic view wing showing the movements 0 when the intermedi for high speed,

he the wing,

adly to aircraft rly to the a1leron is to proor lowern aircraft ailerons attached thereto sic direction, thereg from a high speed to or vice versa, and at the same time differentially varying the travel of is to proolfor the ons in opre lateral objects in view e construction, nt of parts as he accompanying this specification aracters indicate parts throughout the several in which-- Figure l is a top plan view wing showing my invention a Figure 2 is a section t of an aircraft pplied thereto, hrough an aircraft intermediate section and in a high speed Wing, plan view of Figure 1,

Figure 4- is a modified means of adjustintermediate section and still further modification bet an aircraft f the aileron ate section is in position ew showing the when the inter- 1883, AS AMENDED APRIL 30, 1928; 370 0. G. 757) Figure 8 is a detail showing a means of control of the intermediate section, and

Figure 9 is a detail of a means of control of the aileron.

Referring more particularly to the drawings, 1 indicates the body portion of an air craft, and 2 the Wing carried thereby. Although I have illustrated the wing as being the upper one, it will be understood that my invention may be applied to the lower wing or to both the upper and lower Wings. The wing is composed of the main body portion A rigidly constructed about the wing beams 3 and 4. An intermediate section B secured to a shaft 5 that is mounted in bearings 6 supported by the beam 4. Ailerons C are adjustably connected to "the section B through brackets 7. Adjustment of the section B with respect to the wing, A, so that the camber of the aerofoil section of the Wing may be varied, is regulated by an arm 8, one end of which is attached to a born 9 carried by the section B, and the other end of which is made fast to a lever 10 in the cockpit of the aircraft and operable over a segment 11. Lock 12 carried by the leverengages the segment to hold the section B in any desired position of adjustment. It will be understood, how ever, that I do not limit myself to this particular means for imparting movement to the section B, as other arrangements may be successfully used. When movement is imparted to the section B, the ailerons C also move in a like direction, due to their connection with the section B through the brackets 7 The ailerons C, however, have an additional independent movement that is imparted to them through another control mechanism that is also conveniently located in the cockpit of the aircraft. This mechanism consists of a plurality of bars-13 connected with the ailerons at several points along their length, and operated by a control cable 14 that passes over and issecured to suitable pulleys, to which the levers are also attached. The cable consists of a lurality of sections, each succeeding one of which is connected to thepreceding'one in an desired manner, as is shown in Figure 1, an to one of the pulleys 15 by passing loops 16 formed therein over a pin 17 carried by .the pulleys sothat all the ulleys will-move in the direction in whichorceis I app lied'to the cable, as is more clearly shown igure 9. The cable is so arrangedthat the pulleys on opposite sides of the wing will revolve in opposed directions so that one a1le ron will be in a. raised position when the other one is in a lowered position. Each of the pulle s, supported from thegwing beam 3 by brac ets l8, hasan-arm 19 rigidlyconnect'ed theretoso as to move withthe pulley,

The'bars 13 are pivotally connected at one' end to the arms 19 and at the other end to hell crank members 20 that are loosely mounted on the shaft-5, the arm 21 of which operates in a slot 22 formedinarm 23. This arm is attached to theaileron in any suitablemanner and is pivotally connected to the bracket 7, forming a fulcrum about which the arm' ivots when motion is imparted to the bell crank through the bar 13.

In the modification shown in Figure 4, the" same princi le is employed as in the type above described with the following variation in construction; instead of using abell crank operable in a slot formed in an arm attached to the aileron, meshingsegments 24 and 25 are substituted. The segment 25 ismade integral with the arm 20, and like the bell crank in the preferred type, is moved by the bar 13.

. Figure 5 shows a still further modification in which a train of gears 26 is inserted between segments 24 and25.

When the parts are in the position shown in heavy lines in Figure 6, which is the normal. high speed position, a movement of 30 degrees imparted to'the arm 20 will cause the ailerons to move simultaneousl in opposite directions approximately 24 egrees above and below the center line of the wing, as

shown in dotted lines. When, however, the

- ailerons.-

section B and the ailerons have been moved to the position shown in full lines in Figure 7.,

. which is the high lift position, a movement of 30 degrees in the arm 20 will now produce an up-movement of approximately 14degrees in one aileron and a down-movement of approximately 29 degrees in the other aileron relative-to the new neutral position of the It will be understood that the above do scription and accompanying drawings com- Having described my. invention what I claim asnew is 1. In an aircraft wing, the combination of a main section, an intermediate section hinged thereto, ailerons hingedly connected to the intermediate section, meansfor lowering the intermediate section, and means for imparting a differential movement to the ailerons simultaneously with the lowering of the intermediate section.

2. In an aircraft wing, the combination of a main section, an intermediate section hinged thereto, ailerons hingedly connected to the intermediatesection, means for lowering the intermediate section, means for imparting a differential movement to thea'ilerons simultaneously with the loweringof the intermediate section, and means for varying the diflerential'movement of the ailerons with respect to the intermediate section. 3. Inch aircraft wing,

the combination of a main section, an intermediate section hinged thereto, ailerons hingedly connectedfo the intermediate section, means for lowerin the lntermediate section, means for imparting a WALTER s. DIEHL. 

